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Flight Stability And Automatic Control Nelson Solutions -

SM = (xcg - xnp) / c

Substituting the given values, we get:

-0.05 < 0

Therefore, the aircraft is longitudinally stable.

An aircraft has a static margin of 0.2 and a pitching moment coefficient of -0.05. Determine the aircraft's longitudinal stability. Flight Stability And Automatic Control Nelson Solutions

-0.2 > 0 (not satisfied)

Therefore, the aircraft is laterally stable. SM = (xcg - xnp) / c Substituting

where n is the yawing moment.

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Flight Stability And Automatic Control Nelson Solutions